公开(公告)号：KR1020120048439A

公开(公告)日：2012-05-15

申请号：KR1020100110066

申请日：2010-11-05

Applicant: 한국항공대학교산학협력단

Inventor： 곽재수 ,  노영철

IPC: F01D5/20 ,  F01D5/14 ,  F01D11/08

CPC classification number: F01D5/20 ,  F01D5/141 ,  F01D11/08 ,  F02C7/18 ,  F05D2220/32

Abstract: PURPOSE: A gas turbine blade having a squealer tip is provided to improve the durability and the energy efficiency by forming a floor of the squealer tip into an inclined plane so that leakage flows are reduced. CONSTITUTION: A gas turbine blade having a squealer tip comprises a rim. The rim is formed on a front end edge portion of the tip. The squealer tip comprises a cavity inside the rim. A floor of the cavity is formed into an inclined plane. The inclined plane of the floor of the cavity is formed between a sidewall of a pressure surface and the sidewall of a suction surface towards a center. A width of the rim is 1.5 ~ 5% of a length of blade code. The depth from an upper end of the rim to a bottom of the cavity is 1 ~ 6% of a length of a blade span.

Abstract translation: 目的：提供一种具有尖叫尖端的燃气轮机叶片，以通过将尖叫尖端的底板形成倾斜平面来提高耐久性和能量效率，使得泄漏流量减小。 构成：具有尖叫尖端的燃气轮机叶片包括轮辋。 边缘形成在尖端的前端边缘部分上。 尖叫尖端包括边缘内的空腔。 空腔的地板形成倾斜平面。 空腔的底板的倾斜平面形成在压力表面的侧壁和抽吸表面的侧壁之间朝向中心。 边缘的宽度为刀片代码长度的1.5〜5％。 从边缘上端到空腔底部的深度是叶片跨度长度的1〜6％。